Optimisation, design, production, and testing of a topology of an internal actuation system to deflect a seamless morphing leading edge of a wing were proposed.

The actuation system was designed using an aeroelastic optimisation code including sufficient boundary conditions, such as leading edge skin strain allowables, to ensure a practical outcome of the actuation topology. The variation in aero loading during the deflection was taken into account in order not to design the leading edge only for straight and deflected configuration, but to ensure feasibility of the system during transition. The design was translated into a working actuation system which was to be built and tested.

The result of this proposal not only delivered an optimised topology of the actuation system, which was built and tested, for the wing geometry specified by the GRA member, but also provided the ability to quickly develop new actuation architectures for alternative wing geometries.